AD/B717/4 Amdt 2 Rudder Trim Control (Cth)

AIRWORTHINESS DIRECTIVE

On the effective date specified below, and for the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/B717/4 Amdt 1 and issues the following AD under subregulation 39.001(1) of CASR 1998.  The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.

Boeing 717 Series Aeroplanes

AD/B717/4 Amdt 2 Rudder Trim Control 7/2005

Applicability:

Model 717 series aircraft, as listed in Boeing Alert Service Bulletin (ASB) 717-27A0016 Revision 2, or later revision approved by the FAA as an alternative method of compliance (AMOC).

Requirement:

Inspect in accordance with Boeing ASB 717-27A0016 Revision 2 or later revision approved by the FAA as an alternative method of compliance (AMOC).

Note:  FAA AD 2001-18-11 Amdt 39-12437 refers.

Compliance:

As per paragraph (e) of Boeing Alert Service Bulletin (ASB) 717-27A0016 Revision 2, or later revision approved by the FAA as an alternative method of compliance (AMOC).

This Amendment becomes effective on 7 July 2005.

Background:

The FAA received several reports of in-flight binding and/or stiff operation of the rudder trim control system on Model 717 series aircraft.  Subsequent investigation found that approximately 60 rudder trim and load-feel actuators were manufactured with insufficient clearance between the actuator support seal and spring capsule assembly.  Moisture condensing in the area of those components could freeze and cause stiff operation, binding, or jamming of the rudder trim control system and may cause jamming of the rudder.

Amendment 1 was issued in response to a revision of the requirement document, which introduced additional aircraft.  Additionally, the document requires an initial and repeat requirement to lubricate the actuator assembly.

This amendment allows the incorporation of revision 2 of the service bulletin or a later revision, providing it has been approved by the FAA as an acceptable alternative method of compliance.  There is no change to the compliance times.

David Villiers
Delegate of the Civil Aviation Safety Authority

25 May 2005